US4835960A - High compression gas turbine engine - Google Patents

High compression gas turbine engine Download PDF

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Publication number
US4835960A
US4835960A US06/400,759 US40075982A US4835960A US 4835960 A US4835960 A US 4835960A US 40075982 A US40075982 A US 40075982A US 4835960 A US4835960 A US 4835960A
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United States
Prior art keywords
chambers
fuel
gases
rotor
sector
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
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US06/400,759
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English (en)
Inventor
Andzej M. Skoczkowski
Andrew P. Rychlak
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Individual
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Individual
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Priority to US06/400,759 priority Critical patent/US4835960A/en
Priority to CA000432396A priority patent/CA1216160A/en
Priority to EP83304202A priority patent/EP0101206B1/de
Priority to DE8383304202T priority patent/DE3376491D1/de
Priority to JP58133535A priority patent/JPS5968526A/ja
Application granted granted Critical
Publication of US4835960A publication Critical patent/US4835960A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/02—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant
    • F02C5/04—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant the combustion chambers being formed at least partly in the turbine rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the maximum efficiency of the piston engines and the gas turbine is between 30% and 40%; the remaining chemical energy of the fuel is wasted.
  • This invention is directed to providing a novel turbine engine which can be constructed of relatively inexpensive materials and provides a high output beyond that of conventional turbines.
  • the invention comprehends a novel arrangement of components which utilize the chemical energy of the fuel in a more efficient manner than heretofore contemplated, and thus consumes relatively low amounts of fuel.
  • the invention is concerned with providing a turbine engine which has a novel cooling arrangement such as will maintain the internal cycle temperature between 3272° F. (1800° C.) and 3632° F. (2000° C.), by introducing blasts of cool air throughout its inner segments.
  • the invention also has for its object the provision of a simple, compact and light engine.
  • the invention contemplates providing a novel turbine engine which is readily applicable to automobiles, trucks, motor boats and also aircraft.
  • the invention contemplates the production of the novel engine from lightweight metals such as aluminum for the housing, etc.
  • the novel engine is of simple construction and eliminates such conventional components as separate compressors and heat exchangers, and preferably runs on diesel fuel. There is no need for oil changes as in piston engines and the only lubrication required is for lubrication of the shaft bearings.
  • the invention has for its principal object a novel internal combustion system which provides construction of unique turbine and jet turbine engines.
  • FIG. 1 is an elevational view partly in cross-section of the novel engine taken from the intake end thereof, and
  • FIG. 2 is a side elevational view partly in axial section.
  • the engine generally designated R comprises a housing T which has a forwardly flaring tubular air inlet collar 28 at its forward end.
  • the air inlet collar 28 is notched at its rear and comprises a pair of circumferentially spaced flange rings 16, 16 about which there are two resilient half ring gaskets 19, which are biased by two flat springs 21, against a radially extending opposing side wall 13a of a gas generator rotor 13.
  • the air inlet collar 28 is held concentric with the axis of the rotor by means of four or more tear shaped bearing seat supports 20 protruding between the air inlet collar 28 and a face plate cover 18. the face plate cover 18 along with the air inlet collar 28 and the bearing seat supports 20 form a pressure casting.
  • the rotor 13 has a forwardly extending hub which projects into the air inlet collar and is sleeved onto output shaft 6 and made fast thereto in any conventional manner.
  • the rotor 13 has a plurality of radially extending chambers 15 which are defined by annular front wall 14a and a series of circumferentially spaced radial blades 14 which connect the wall 14a with rotor wall 13a. It will be apparent that the wall 14a converges outwardly with wall 13a toward the outer outlet ends 13b of rotor 13.
  • the outlet ends 13b lead into gas collectors 3, which form part of a power receptor and are fastened to the face plate 18 and to rings 23 and 25 and to an exhaust manifold 5. Air is aspirated into the combustion chambers 15 from the air intake 4 through diametrically spaced notches K between the ends of the split rings 16,16, into the center of the rotor 13 by centrifugal action.
  • the collectors 3 comprise a circumferentially spaced series of blades 2 which form passages 30.
  • the blades 2 provide inlets 3b of the collectors 3 communicating with the outlet ends 13b of the rotor 13 and direct high pressure exhaust gases from main combustion chambers 15 through a series of axially directed passages 9a defined by blades 9 in a first turbine rotor 29 which is also part of the power receptor.
  • the rotor 29 is fastened to the shaft 6.
  • the gasses are directed by the turbine blades 9 against guide vanes 10 of a stator ring 24 (also part of the power receptor) disposed coaxially with the front and rear rotors 29, 29a forming another part of the power receptor. Subsequently gases continue discharge against turbine blades 9c of the rear rotor 29a which is fastened to the shaft 6.
  • Each ignition system comprises one gas ignition chamber 1, also called a precombustion chamber, one fuel injector 12, one glow plug 11 and one fuel distribution or intake channel M.
  • the engine is started by cranking the shaft 6 with an electric starter coupled thereto in conventional manner, just as in diesel engines.
  • the air enters that section of chambers 15 which are located in the sector E-G of the engine circumference.
  • Sector E-G is divided into two sections E-F and F-G.
  • E-F section said air, being of ambient temperature is accelerated radially outwardly by centrifugal vorce, cools the walls of the components through which it passes including: the walls of the main combustion chambers 15, the walls of the collector 3, collector vanes 2, turbine blades 9, 9c and guide vanes 10.
  • this phase comprises the inner cooling of the engine.
  • the cool air flows through the hot parts of the engine through which the heated gases of combustion subsequently flow.
  • the sector D-E is where the highly compressed gases and discharged through the passages 30 in collectors 3 into the front turbine blades 9, the guide vanes 10 and the rear turbine blades 9c, and discharge into the exhaust manifold 5.
  • the pressure of the exhaust gases in the combustion chambers 15 is very near to atmospheric pressure. Thereafter the exhausted chambers 15 align with the appropriate notch K. New air is then aspirated into these chambers 15 and the cycle is repeated.
  • T 1 --293° K. (20° C.) Ambient Temp.
  • Our new diesel gas tturbine engine has two separate ignition systems. Each of them consists of one gas ignition chamber 1, one fuel injector 12 and a glow plug 11. In this type of high compression engine use has been made of a conventional glow plug, which is commonly used in most high compression diesel engines.
  • the glow plugs 11 are switched on before starting the engine and remain on only until the gas is fired and the engine starts and thereafter the plugs are turned off.
  • the fuel injectors inject the fuel under high pressure in an atomized state directly into the gas ignition chambers 1. This process of fuel injection 12 continues until the engine is turned off.
  • the gas ignition chambers 1 are very important segments of this engine. Their parameters have very high influence on engine performance. In the gas ignition chambers 1 phase one of the ignition process called “delayed combustion" takes place. Here, a minimal change in temperature and pressure results and a slow burn of the fuel occurs, vbecause of the low oxygen content.
  • the high pressure exhaust gases entering chamber 1 through port 1a transfer the slow burning gas mixture through the gas passage 17 and port 17a into the main combustion chambers 15.
  • the oncoming main combustion chambers 15 are being filled with pressurized cool oxygen-enriched air.
  • the temperature which is high, and pressurized oxygen enriched air, causes combustion many times faster in the main combustion chambers 15 than in any other conventional combustion engine.
  • suitable dimensions of cross-sections of the gas chamber passages 17 it is possible to widely vary the secondary compression ratio in conjunction with the fuel used and the purpose of the engine.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Supercharger (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Valve Device For Special Equipments (AREA)
  • Pulleys (AREA)
US06/400,759 1982-07-22 1982-07-22 High compression gas turbine engine Expired - Fee Related US4835960A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US06/400,759 US4835960A (en) 1982-07-22 1982-07-22 High compression gas turbine engine
CA000432396A CA1216160A (en) 1982-07-22 1983-07-13 High compression gas turbine engine
EP83304202A EP0101206B1 (de) 1982-07-22 1983-07-20 Hochverdichtender Gasturbinenmotor
DE8383304202T DE3376491D1 (en) 1982-07-22 1983-07-20 High compression gas turbine engine
JP58133535A JPS5968526A (ja) 1982-07-22 1983-07-21 内燃ロ−タリエンジン

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/400,759 US4835960A (en) 1982-07-22 1982-07-22 High compression gas turbine engine

Publications (1)

Publication Number Publication Date
US4835960A true US4835960A (en) 1989-06-06

Family

ID=23584888

Family Applications (1)

Application Number Title Priority Date Filing Date
US06/400,759 Expired - Fee Related US4835960A (en) 1982-07-22 1982-07-22 High compression gas turbine engine

Country Status (5)

Country Link
US (1) US4835960A (de)
EP (1) EP0101206B1 (de)
JP (1) JPS5968526A (de)
CA (1) CA1216160A (de)
DE (1) DE3376491D1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060177302A1 (en) * 2005-02-04 2006-08-10 Berry Henry M Axial flow compressor
US20100107647A1 (en) * 2008-10-30 2010-05-06 Power Generation Technologies, Llc Toroidal boundary layer gas turbine
US20140007837A1 (en) * 2012-07-09 2014-01-09 Isaac Erik Anderson Shockwave Rotor Detonation (Omni-Engine, Ubiquitous X engine) Multipurpose Engine
WO2014130697A1 (en) * 2013-02-20 2014-08-28 University Of Southern California Transient plasma electrode for radical generation
US9052116B2 (en) 2008-10-30 2015-06-09 Power Generation Technologies Development Fund, L.P. Toroidal heat exchanger
US9377002B2 (en) 2013-02-20 2016-06-28 University Of Southern California Electrodes for multi-point ignition using single or multiple transient plasma discharges
CN109779744A (zh) * 2019-04-08 2019-05-21 重庆必优得科技发展有限公司 转子发动机

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1388707A (en) * 1918-10-01 1921-08-23 John O Heinze Turbine
US2448972A (en) * 1944-10-20 1948-09-07 Edward W Gizara Internal-combusstion engine
US2705867A (en) * 1949-06-30 1955-04-12 Curtiss Wright Corp Engine having a rotor with a plurality of circumferentially-spaced combustion chambers
US3057157A (en) * 1959-10-08 1962-10-09 William D Close Rotary engine
US3150646A (en) * 1961-08-07 1964-09-29 Bernard John Springer Rotary engine apparatus
US3200588A (en) * 1963-02-26 1965-08-17 Friedrich C Math Jet reaction motor
US3224711A (en) * 1963-04-19 1965-12-21 Henry R Warren Heavier-than-air aircraft
US3321911A (en) * 1965-02-12 1967-05-30 Myles Tommie Lynn Gas turbine engine with rotating combustion chamber
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
GB2017222A (en) * 1978-03-20 1979-10-03 Chair R S De Gas Turbine Unit
DE2840662A1 (de) * 1978-09-19 1980-04-03 Exner Technik Fuer Ind Und Ber Kleingasturbine, bestehend aus einer, wechselweise mit kaltluft und heissgas beaufschlagten scheibe

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB220307A (en) * 1923-08-06 1924-11-20 Carl Ferdinand Leich Internal combustion turbine
DE522435C (de) * 1927-08-17 1931-04-09 E H Hans Holzwarth Dr Ing Verpuffungskammer, insbesondere fuer Brennkraftturbinen
US2928239A (en) * 1954-03-16 1960-03-15 Arthur W Goldstein Impelled charge gas explosion turbine with constant volume, pressure raising combustion chambers
US3899874A (en) * 1974-09-11 1975-08-19 Henry E Bailey Turbine engine
US4241576A (en) * 1979-01-15 1980-12-30 Gertz David C Gas turbine engine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1388707A (en) * 1918-10-01 1921-08-23 John O Heinze Turbine
US2448972A (en) * 1944-10-20 1948-09-07 Edward W Gizara Internal-combusstion engine
US2705867A (en) * 1949-06-30 1955-04-12 Curtiss Wright Corp Engine having a rotor with a plurality of circumferentially-spaced combustion chambers
US3057157A (en) * 1959-10-08 1962-10-09 William D Close Rotary engine
US3150646A (en) * 1961-08-07 1964-09-29 Bernard John Springer Rotary engine apparatus
US3200588A (en) * 1963-02-26 1965-08-17 Friedrich C Math Jet reaction motor
US3224711A (en) * 1963-04-19 1965-12-21 Henry R Warren Heavier-than-air aircraft
US3321911A (en) * 1965-02-12 1967-05-30 Myles Tommie Lynn Gas turbine engine with rotating combustion chamber
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
GB2017222A (en) * 1978-03-20 1979-10-03 Chair R S De Gas Turbine Unit
DE2840662A1 (de) * 1978-09-19 1980-04-03 Exner Technik Fuer Ind Und Ber Kleingasturbine, bestehend aus einer, wechselweise mit kaltluft und heissgas beaufschlagten scheibe

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
Carlstrom et al, "Improved Emissions Performance in Today's Combustion System", International Seminar, AEG/SOA, 6-78, p. 17.
Carlstrom et al, Improved Emissions Performance in Today s Combustion System , International Seminar, AEG/SOA, 6 78, p. 17. *

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060177302A1 (en) * 2005-02-04 2006-08-10 Berry Henry M Axial flow compressor
US20100107647A1 (en) * 2008-10-30 2010-05-06 Power Generation Technologies, Llc Toroidal boundary layer gas turbine
US8863530B2 (en) 2008-10-30 2014-10-21 Power Generation Technologies Development Fund L.P. Toroidal boundary layer gas turbine
US9052116B2 (en) 2008-10-30 2015-06-09 Power Generation Technologies Development Fund, L.P. Toroidal heat exchanger
US9243805B2 (en) 2008-10-30 2016-01-26 Power Generation Technologies Development Fund, L.P. Toroidal combustion chamber
US10401032B2 (en) 2008-10-30 2019-09-03 Power Generation Technologies Development Fund, L.P. Toroidal combustion chamber
US20140007837A1 (en) * 2012-07-09 2014-01-09 Isaac Erik Anderson Shockwave Rotor Detonation (Omni-Engine, Ubiquitous X engine) Multipurpose Engine
US9970294B2 (en) * 2012-07-09 2018-05-15 Isaac Erik Anderson Shockwave rotor detonation (omni-engine, ubiquitous X engine) multipurpose engine
WO2014130697A1 (en) * 2013-02-20 2014-08-28 University Of Southern California Transient plasma electrode for radical generation
US9377002B2 (en) 2013-02-20 2016-06-28 University Of Southern California Electrodes for multi-point ignition using single or multiple transient plasma discharges
CN109779744A (zh) * 2019-04-08 2019-05-21 重庆必优得科技发展有限公司 转子发动机
CN109779744B (zh) * 2019-04-08 2024-02-02 重庆必优得科技发展有限公司 转子发动机

Also Published As

Publication number Publication date
JPS5968526A (ja) 1984-04-18
CA1216160A (en) 1987-01-06
EP0101206A1 (de) 1984-02-22
DE3376491D1 (en) 1988-06-09
EP0101206B1 (de) 1988-05-04

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Effective date: 19930606

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362